Abstract: A structure of an electric aircraft is disclosed. The structure may include a wing, wherein the wing is a single component that runs from a left side of the electric aircraft to a right side of the electric aircraft. The wing may include an airfoil. The structure may include at least a boom, wherein the at least a boom is configured to carry at least a propulsor. The at least a boom may include a boom joint attached to the wing. The at least a boom may further include at least a first boom segment attached to a first end of the boom joint. The at least a boom may further include at least a second boom segment attached to a second end of the boom joint.

Abstract: A structure of an electric aircraft is disclosed. The structure may include a wing, wherein the wing is a single component that runs from a left side of the electric aircraft to a right side of the electric aircraft. The wing may include an airfoil. The structure may include at least a boom, wherein the at least a boom is configured to carry at least a propulsor. The at least a boom may include a boom joint attached to the wing. The at least a boom may further include at least a first boom segment attached to a first end of the boom joint. The at least a boom may further include at least a second boom segment attached to a second end of the boom joint.

Abstract: A method of forming a composite structure having a skin, a plurality of webs and a plurality of flanges includes wrapping each of a plurality of first lay-ups around a corresponding one of a plurality of mandrels such that each first lay-up forms a skin section, a pair of opposed web sections, which extend from the skin section, and a pair of inwardly facing flange sections. The first lay-ups are aligned and a second lay-up is laid over their skin sections. A plurality of third lay-ups are laid over pairs of flange sections. A composite structure detained by this method is also disclosed.